| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 可随地起飞降落的飞机 | CN201610301996.9 | 2016-05-02 | CN107336834A | 2017-11-10 | 郭钟 |
| 本发明涉及一种交通运输工具，它有着和普通平飞飞机一样的外貌却可以实现垂直起飞和降落。本发明的目的是为了实现现今飞机能在较差地面降落而提出的一种问题解决方案。它的机身重心在飞行中可以通过操作做前后的部分移动来使机身的飞行状态在水平和垂直间变化。它的尾翼要处于发动机吹出的气流中或由专门设计的可收缩的尾部螺旋桨来控制飞机降落中的水平位移方向从而选择降落地点。它的机身装有由陀螺仪和计算机控制的机身平衡稳定系统和伺服控制系统来操控带有传感器并可展开的有一定接地面积且没有轮子的起落架。 | ||||||
| 2 | 磁気方向付けディテント機構 | JP2017022755 | 2017-02-10 | JP2017159888A | 2017-09-14 | ダスティン エリ ギャンブル |
| 【課題】ハイブリッド航空機の空力特性を高めることができる、磁気方向付けディテント機構を提供する。 【解決手段】一実施形態では、ハイブリッド航空機は、固定翼推進システム及びマルチロータ推進システムを含む。マルチロータ推進システムは、モータシャフトに結合されたプロペラを含む。モータは、モータシャフトを介してプロペラを駆動する。ハイブリッド航空機は、マルチロータ推進システムへの動力が除去される際にマルチロータ推進システムのプロペラが回転することを防止するための磁気方向付けディテント機構を含む。磁気方向付けディテント機構は、モータシャフトの周囲に結合された複数の磁石と、複数の磁石に磁気的に結合されるディテント磁石とをさらに含む。 【選択図】図3A |
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| 3 | It does not have a rotary-wing vertical take-off and landing aircraft | JP2009529729 | 2007-09-10 | JP2010504249A | 2010-02-12 | アギラール，ミシェル |
| 本発明は、二つのターボジェットエンジン（１）から構成される垂直離陸を行なう航空機に関するものであり、タービンエンジンの長方形のセクションの吸気口（２）は圧縮された空気をタンクに供給する回転容積型の圧縮機（３）上で開き、該タンクは一方では燃焼室と連結し、その後に燃焼ガスは圧縮機（３）を連動させるタービン（４）を作動させ、そして固定された後翼の翼の上面（５）に噴出されるものであり、他方では主要エンジンの燃焼室（６）と連結し、その燃焼ガスは、取り付け角が可変で、離陸時には揚力を生むようにして据え付けられる翼（８）の上面（７）に直接噴出される。 そしてこれに正確かつ可変の翼上面（９）を有する前翼で生まれる揚力が加わる。 この翼上面は離陸モードでは最大に湾曲し、その上面に前翼の内部にある燃焼室で生み出された燃焼ガスが高速で流れる。 周遊モードではこの燃焼室の火は消えており、翼上面（９）はこのとき湾曲の角度が減少されたものに戻る。 同時に後翼（８）は揚力と全体の抵抗力が最適化するような取り付け角になる。 本発明による航空機は空路での乗客の運搬に特に適している。
【選択図】図１ |
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| 4 | BOGIE MECHANISM FOR A TILTROTOR PROPROTOR DOOR | EP17197649.1 | 2017-10-20 | EP3369659A1 | 2018-09-05 | PRAVANH, Nick; RINEHART, Michael E; SHAFER, Bart; SMITH, Clegg; WILLIAMS, Jeffrey M |
A door roller mechanism (214) for cooperation with a roller track (212) including a carriage member (215) having a door attachment feature (217); at least one roller (216) disposed for rotation on a first side (215f) of the carriage member (215) when the carriage member (215) moves in the rolling direction (RD); at least one roller (216) disposed for rotation on an opposite second side (215d) of the carriage member (215) when the carriage member (215) moves in the rolling direction (RD); a first rub member (230) disposed on the first side (215f) of the carriage; a second rub member (232) disposed on the second side (215d) of the carriage; and at least one biasing element (234) disposed on the carriage member (215) for resiliently biasing the first rub member (230) and the second rub member (232) in opposite lateral directions so as to contact a respective first track surface (320d, 322d) and a second track surface (320e, 322e) in a manner to dampen lateral vibration of a door (204) connected to the roller mechanism (214).
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| 5 | JPS5037200A - | JP7275574 | 1974-06-25 | JPS5037200A | 1975-04-07 | |
| 6 | JPS5037199A - | JP7275474 | 1974-06-25 | JPS5037199A | 1975-04-07 | |
| 7 | ROLLER TRACK ASSEMBLY FOR A TILTROTOR PROPROTOR DOOR | EP17197812.5 | 2017-10-23 | EP3378767A1 | 2018-09-26 | PRAVANH, Nick; RINEHART, Michael E.; SHAFER, Bart; SMITH, Clegg; BACON, Bruce B. |
A door track assembly for cooperation with a door roller mechanism (214), including a housing (300) having a longitudinal channel (304) along a length of the housing (300), wherein the channel (304) descends at an end of the housing to form a stowage recess (304b) for the door roller mechanism (214), and a first track (320) and a second track (322) that are disposed on the housing (300) along a length of the channel (304) and that descend into the stowage recess (304b) and along which the door roller mechanism (214) traverses.
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| 8 | VEHICULE A DECOLLAGE ET ATTERRISSAGE VERTICAL SANS VOILURE TOURNANTE | EP07823490.3 | 2007-09-10 | EP2066564B1 | 2010-09-15 | AGUILAR, Michel |
| 9 | VEHICULE A DECOLLAGE ET ATTERRISSAGE VERTICAL SANS VOILURE TOURNANTE | EP07823490.3 | 2007-09-10 | EP2066564A1 | 2009-06-10 | AGUILAR, Michel |
| The invention relates to a vertical take-off vehicle including two thermoreactors (1) or turbine engines having a rectangular air inlet (2) which opens into a positive-displacement rotary compressor (3) that supplies compressed air to a tank which is connected to (i) a combustion chamber, the exhaust gases from which actuate a compressor-driving turbine (4) and are then discharged onto the upper surface (5) of the fixed rear wing, and (ii) the combustion chamber of the main engine (6), the exhaust gases from which are discharged directly onto the upper surface (7) of the wing (8), the variable incidence of which, in take-off mode, is set to generate a lift force which is added to the forces that develop on the front wings. In take-off mode, the variable-geometry upper surfaces (9) of the aforementioned front wings have a maximum camber onto which the exhaust gases produced in an internal combustion chamber located thereat flow at great speed. In cruise mode, said combustion chamber is switched off and the upper surface (9) returns to a reduced camber position as the rear wing (8) is returned to an incidence whereby the total drag and lift forces are optimised. According to the invention, the vehicle is particularly suitable for transporting passengers by air. | ||||||
| 10 | 로터가 숨겨진 하이브리드 수직이착륙 무인항공기 | KR1020160097161 | 2016-07-29 | KR101772223B1 | 2017-08-28 | 민경무; 니케시브하타라이; 치아풍이 |
| 본발명은로터가숨겨진하이브리드수직이착륙무인항공기에관한것으로보다상세하게는항공기의수평비행시에는항공기의내부에숨겨지고, 수직비행시에노출되어작동하는로터가숨겨진하이브리드수직이착륙무인항공기에관한것이다. 본발명에따른로터가숨겨진하이브리드수직이착륙무인항공기는, 항공기의동체역할을하는몸체; 상기몸체의양측에마련되고, 상기몸체로부터수직방향으로회전가능하도록형성되는날개; 상기날개의양단부에마련되는윙렛; 상기날개의내부에마련되고, 상측방향으로추진력을발생하는전방로터; 상기몸체의후방에마련되어, 전방및 상방으로추진력을발생하는후방로터; 및상기몸체의내부에마련되고, 상기날개및 후방로터를회전시키는구동부;를포함하고, 상기구동부에의하여상기날개가수직방향으로회전하면상기날개의내부에위치되는상기전방로터가외부로노출되는것을특징으로한다. 본발명의일실시예에따르면수직비행시에날개를수직방향으로회전시켜전방로터가노출되도록하고, 수평비행시에전방로터가숨겨지게함으로써, 수평비행시에전방로터에의하여항력이발생되는것을방지할수 있는로터가숨겨진하이브리드수직이착륙무인항공기가제공된다. 또한, 날개의양단부에수직안정판(Vertical Stabilizer) 역할과윙팁에서의유도항력을줄이는역할을동시에하는윙렛을설치함으로써, 항공기의후방에별도의수직안정판을설치하지않아도되는로터가숨겨진하이브리드수직이착륙무인항공기가제공된다. 또한, 수직이착륙시에윙렛을회전시켜착륙장치역할을할 수있는로터가숨겨진하이브리드수직이착륙무인항공기가제공된다. | ||||||
| 11 | 자기 배향 멈춤쇠 | KR1020170017975 | 2017-02-09 | KR1020170094518A | 2017-08-18 | 겜블엘리더스틴 |
| 일실시예에서, 하이브리드항공기는고정익추진시스템및 다중로터추진시스템을포함한다. 다중로터추진시스템은모터샤프트에결합된프로펠러를포함한다. 모터는모터샤프트를통해프로펠러를구동한다. 하이브리드항공기는다중로터추진시스템으로의동력이제거되면다중로터추진시스템의프로펠러가회전하는것을방지하기위한자기배향멈춤쇠를더 포함한다. 자기배향멈춤쇠는모터샤프트의원주에결합된복수의자석및 복수의자석에자기적으로결합되는멈춤쇠자석을더 포함한다. | ||||||
| 12 | 무선 조종 비행체 어셈블리 | KR20160172870 | 2016-12-16 | KR20180070310A | 2018-06-26 | GWAK JUN BEOM |
| 본발명은무선조종비행체어셈블리를제공한다. 본발명의실시예에의한무선조종비행체어셈블리의일 양태는, 바디부, 상기바디부의전단에구비되는프로펠러, 상기바디부의양측에수평방향으로구비되는한쌍의주 날개및 한쌍의수평꼬리날개및상기바디부의상면에수직방향으로구비되는수직꼬리날개를포함하는비행기; 상기비행기의외측에배치되는이너링; 상기이너링의외측에배치되는미들링; 상기미들링의외측에배치되는다수개의아웃터링; 상기바디부의길이방향에직교되는방향으로상기바디부를관통한상태에서그 양단이상기이너링의내면에고정되는제1축; 상기이너링의외면에그 일단이회전가능하게연결되고, 상기미들링의내면에그 타단이회전가능하게연결되는제2축; 및상기미들링의외면에그 일단이회전가능하게연결되고, 상기아웃터링의내면에그 타단이회전가능하게연결되는제3축; 을포함하고, 상기프로펠러의구동에의하여추력이발생하면, 적어도상기미들링에대한상기아웃터링의회전에의하여상기아웃터링이지면을따라서구름운동하여상기비행기가활주이륙하거나, 적어도상기이너링에대한상기비행기의회전에의하여상기비행기가수직이륙한다. | ||||||
| 13 | 비행접시 | KR1020040079998 | 2004-10-07 | KR1020060031105A | 2006-04-12 | 김이섭 |
| 본 고안발명은 팬을 이용해 공기를 흡입하며 비행체의 지붕 곡면을 따라 흐르는 공기흐름에 의해 발생하는 저압에 의해발생하는 부양력을 이용해 비행하는 비행법시에 관한 발명이다. 비행접시,팬, 공기흡입구, 공기배출구 | ||||||
| 14 | Multiple motor gas turbine engine system with auxiliary gas utilization | US13998564 | 2013-11-12 | US09777698B2 | 2017-10-03 | Daniel Keith Schlak |
| A vehicle propulsion system comprises at least two motors. Combustion occurs upstream of a first motor, and a second motor is downstream of said first motor. The first motor is a turbine that drives a primary propulsion element to effect propulsion and a compressor to effect compression. The second motor is an expansion device whose incoming gases arrive from said first motor. The first motor and the second motor intercommunicate energy via electrical, electromagnetic, and/or mechanical means. Pressurized gases that result from said compression, combustion, or both are rendered or wastegated for auxiliary usage such as aerial thrust, vertical takeoff and/or vertical landing, near-vertical takeoff and/or near-vertical landing, pneumatic storage for hybrid drive, pneumatic lift and/or drive for towing and/or raising another vehicle, aerial vehicle steering, aerial vehicle pitch stabilization or manipulation, aerial vehicle roll stabilization or manipulation, and/or aerial vehicle yaw stabilization or manipulation. | ||||||
| 15 | System, apparatus and method for long endurance vertical takeoff and landing vehicle | US14507313 | 2014-10-06 | US09682774B2 | 2017-06-20 | James Donald Paduano; Paul Nils Dahlstrand; John Brooke Wissler; Adam Woodworth |
| A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | ||||||
| 16 | AUTOMOTIVE DRONE DEPLOYMENT SYSTEM | US15419804 | 2017-01-30 | US20170139420A1 | 2017-05-18 | John A. Lockwood; Joseph F. Stanek |
| This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced. | ||||||
| 17 | AUTOMOTIVE DRONE DEPLOYMENT SYSTEM | US15231579 | 2016-08-08 | US20160347452A1 | 2016-12-01 | Joe F. Stanek; John A. Lockwood |
| This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced. | ||||||
| 18 | SYSTEM AND METHOD FOR IMPROVING TRANSITION LIFT-FAN PERFORMANCE | US14278044 | 2014-05-15 | US20160144956A1 | 2016-05-26 | ROBERT PARKS |
| A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off. | ||||||
| 19 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE | US14507313 | 2014-10-06 | US20150336663A1 | 2015-11-26 | JAMES DONALD PADUANO; PAUL NILS DAHLSTRAND; JOHN BROOKE WISSLER; ADAM WOODWORTH |
| A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | ||||||
| 20 | Aircraft control methods | US37442973 | 1973-06-28 | US3831887A | 1974-08-27 | FOSNESS J |
| Method of apparatus operation are disclosed for advantageously developing fluid-reaction lift control and also attitude control in improved manners in aircraft systems of the type capable of vertical, hovering, transitional, and conventional modes of flight operation. The apparatus consists of an aircraft system having an airframe with right and left primary airfoils and right and left canard airfoils, spaced-apart forward and after rotatable flap members in each airfoil which define a lift ejector diffuser section having a divergence angle, an engine operable at different rotational speeds to produce different corresponding high-energy primary fluid flows and a duct system for selectively distributing the total primary fluid flow from the engine to the lift ejector diffuser sections in each airfoil. The method of operating the control system comprises the steps of: operating the engine at a constant rotational speed and output power to produce a total primary fluid flow; distributing the total primary fluid flow to the lift ejector diffuser sections in proportions divided equally between said right and left airfoils; and changing the altitude or attitude of the aircraft by rotating the forward and after flap members in opposite directions with respect to each other in each of the airfoils to change the lift ejector divergence angles while the rotational speed, output power and total primary fluid flow of the engine and the proportional distribution of the total primary fluid flow remains constant.
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